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由于机翼为主承力结构,蒙皮修理主要采用机械连接修理方式,针对民机复合材料机翼下蒙皮壁板结构的离散源损伤开展了修理方案设计、试验验证、有限元分析及改进设计研究。首先,根据损伤类型和下蒙皮壁板的传载特性,设计了机械连接金属补片修理方案,并制造了包括含损伤和损伤修理两类试验件,进行了试验验证,修理后承载能力提高了124%,能够满足一般民机复合材料机翼蒙皮设计许用应变。然后,建立了两类试验件的有限元模型,进行了进一步计算分析,通过对试验数据和计算结果的对比分析发现,原修理方案偏于保守,增加了结构重量成本。最后,经计算分析提出了三种改进的修理设计方案,改进后的修理构型II承载能力相对于原修理方案提高了4.7%,而结构重量降低了3.9%,该修理方法可为今后民机复合材料机翼修理方案的设计提供参考。
Because of the main bearing structure of the wing, the repair of the skin is mainly carried out by means of mechanical connection repair. The repair scheme design, experimental verification, finite element analysis and design improvement are carried out for the discrete source damage of the skin panel structure under the wing of the civil aircraft composite the study. First of all, according to the type of damage and the transmission characteristics of the lower skin panel, a mechanical repair scheme of the metal patch is designed, and two types of test pieces including damage and damage repair are manufactured, tested, and the carrying capacity is improved after the repair 124%, to meet the general civil aircraft composite wing skin design allowable strain. Then, the finite element model of two types of test pieces was established and further calculation and analysis were carried out. By comparing the test data with the calculated results, it was found that the original repair plan was conservative and the cost of the structure was increased. Finally, three improved repair plans are proposed through calculation and analysis. The carrying capacity of the improved repair configuration II is increased by 4.7% compared with that of the original repair plan and the weight of the structure is reduced by 3.9%. The repair method can be used for future civil aircraft Composite wing repair program design for reference.